U.S. patent application number 14/947785 was filed with the patent office on 2017-05-25 for detection of deficient sensors in a gas turbine system.
The applicant listed for this patent is John Thomas Cutright, Nicolas Demougeot, SUMIT SONI. Invention is credited to John Thomas Cutright, Nicolas Demougeot, SUMIT SONI.
Application Number | 20170145851 14/947785 |
Document ID | / |
Family ID | 58720180 |
Filed Date | 2017-05-25 |
United States Patent
Application |
20170145851 |
Kind Code |
A1 |
SONI; SUMIT ; et
al. |
May 25, 2017 |
DETECTION OF DEFICIENT SENSORS IN A GAS TURBINE SYSTEM
Abstract
Methods and systems for determining that a sensor, such as a
pressure sensor, that provides feedback on one or more conditions
of a gas turbine is deficient are provided. The amplitude of
measurements from the sensor may be monitored in different
frequency ranges in order to detect certain abnormal conditions of
the gas turbine that require attention by the control system in one
frequency range, and also, concurrently and/or separately, detect a
sensor deficiency in another frequency range prior to actual
failure of the sensor, at which time the failure may otherwise be
noticeable in the first frequency range. This permits better
detection of deficient sensors during operation of the gas
turbine.
Inventors: |
SONI; SUMIT; (Jupiter,
FL) ; Cutright; John Thomas; (Stuart, FL) ;
Demougeot; Nicolas; (Stuart, FL) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
SONI; SUMIT
Cutright; John Thomas
Demougeot; Nicolas |
Jupiter
Stuart
Stuart |
FL
FL
FL |
US
US
US |
|
|
Family ID: |
58720180 |
Appl. No.: |
14/947785 |
Filed: |
November 20, 2015 |
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F05D 2270/80 20130101;
G01M 15/14 20130101; G01L 27/007 20130101; F01D 21/14 20130101;
F01D 21/003 20130101; F02C 9/00 20130101; F05D 2260/80
20130101 |
International
Class: |
F01D 21/00 20060101
F01D021/00; G01L 27/00 20060101 G01L027/00; G01M 15/14 20060101
G01M015/14; F02C 3/04 20060101 F02C003/04 |
Claims
1. A computer-implemented method, executed by one or more
processors, for detecting deficient sensors in gas turbines, the
method comprising: receiving pressure readings from a pressure
sensor coupled to a gas turbine; monitoring a first frequency range
of the pressure readings for abnormal conditions of the gas
turbine; monitoring a second frequency range of the pressure
readings for sensor failure indications; and determining either
that: the sensor failure indications are not present and that the
monitoring for the abnormal conditions is being performed by a
correctly operating sensor, or the sensor failure indications are
present and that the monitoring for the abnormal conditions is
being performed by a deficient sensor.
2. The method of claim 1, wherein: the abnormal conditions comprise
a first range of sensor readings or a minimum sensor reading in the
first frequency range, and the sensor failure indications comprise
a second range of sensor readings in the second frequency
range.
3. The method of claim 2, wherein the first range of sensor
readings and the second range of sensor readings are either: at
least partially overlapping; or non-overlapping.
4. The method of claim 2, wherein the first frequency range, the
second frequency range, the first range of sensor readings, and the
second range of sensor readings are user-configurable.
5. The method of claim 1, wherein the abnormal conditions comprise
a pressure spike above a predetermined minimum pressure
reading.
6. The method of claim 1, wherein the first frequency range is
higher than the second frequency range.
7. The method of claim 1, further comprising detecting that the
sensor failure indications have occurred, wherein upon detecting
that the sensor failure indications have occurred, performing at
least one of: ignoring input from the pressure sensor; disabling
input from the pressure sensor; and providing an indication that
the pressure sensor is deficient.
8. The method of claim 1, further comprising detecting that the
sensor failure indications have occurred, wherein determining that
the sensor failure indications have occurred comprises determining
that a first pressure signal amplitude from the first frequency
range and a second pressure signal amplitude from the second
frequency range are at least a predetermined difference, and
wherein the second pressure signal amplitude is greater than the
first pressure signal amplitude.
9. The method of claim 1, wherein the first frequency range is at
least 10 Hz on its lowest end, and wherein the second frequency
range is at most 10 Hz on its upper end.
10. The method of claim 1, wherein monitoring for the abnormal
conditions and monitoring for the sensor failure indications occurs
concurrently.
11. One or more computer-readable media having computer executable
instructions embodied thereon that, when executed, perform a method
for detecting deficient sensors in gas turbines, the method
comprising: receiving signals from a sensor in a gas turbine;
monitoring a first frequency range of the signals for abnormal
conditions of the gas turbine; monitoring a second frequency range
of the signals for sensor failure indications; and determining
either that: the sensor failure indications are not detected and
the sensor is operating correctly, or the sensor failure
indications are detected and the sensor is deficient, wherein the
abnormal conditions comprise a first range of sensor readings in
the first frequency range, and wherein the sensor failure
indications comprise at least one of: a minimum sensor reading in
the second frequency range, and a minimum difference between
concurrent sensor readings in the first frequency range and in the
second frequency range.
12. The media of claim 11, wherein the sensor is a pressure sensor,
and wherein monitoring the first frequency range and monitoring the
second frequency range comprises monitoring a signal amplitude in
the respective frequency ranges.
13. The media of claim 11, wherein the first frequency range is a
minimum of 10 Hz at its lowest end, and wherein the second
frequency range is a maximum of 10 Hz at its upper end.
14. The media of claim 11, further comprising detecting that the
sensor failure indications have occurred, wherein upon detecting
that the sensor failure indications have occurred, performing at
least one of: ignoring input from the sensor; disabling input from
the sensor; and providing an indication that the sensor is
deficient.
15. The media of claim 11, wherein determining that the abnormal
conditions have occurred comprises determining that the sensor is
providing at least a predetermined signal amplitude in the first
frequency range, and wherein determining that the sensor failure
indications have occurred comprises determining that the sensor is
providing at least a predetermined signal amplitude in the second
frequency range.
16. A system for detecting deficient sensors in gas turbines, the
system comprising: a gas turbine having one or more combustors; a
control system communicatively coupled to the gas turbine; a sensor
coupled to the gas turbine and communicatively coupled to the
control system, the sensor sending signals to the control system;
and wherein the control system is configured to: monitor a first
frequency range of the signals for abnormal conditions of the gas
turbine; monitor a second frequency range of the signals for sensor
failure indications; and determine either that: the sensor failure
indications are not detected and the sensor is operating correctly,
or the sensor failure indications are detected and the sensor is
deficient, wherein the abnormal conditions comprise a first range
of sensor readings in the first frequency range, wherein the sensor
failure indications comprise a second range of sensor readings in
the second frequency range, and wherein the first frequency range
is higher than the second frequency range.
17. The system of claim 16, wherein the sensor is a pressure sensor
that provides pressure readings to the control system, and wherein
the control system monitors a relative difference between
concurrently measured signal amplitudes from the pressure sensor in
the first frequency range and in the second frequency range.
18. The system of claim 16, further comprising a plurality of
pressure sensors coupled to the gas turbine, wherein the control
system compares pressure readings received from the plurality of
pressure sensors.
19. The system of claim 16, wherein: the abnormal conditions
comprise a minimum signal amplitude in the first frequency range,
and the sensor failure indications comprise a minimum signal
amplitude in the second frequency range.
20. The system of claim 16, wherein the first frequency range is at
least 10 Hz on its lowest end, and wherein the second frequency
range is at most 10 Hz on its upper end.
Description
TECHNICAL FIELD
[0001] The field of the invention relates to gas turbines and their
associated control systems and sensors.
BACKGROUND OF THE INVENTION
[0002] Gas turbines operate to produce mechanical work or thrust,
and are typically coupled to a generator for producing electricity.
The drawing of electrical current from the generator causes a load
to be applied to the gas turbine. This load is essentially a
resistance that the gas turbine must overcome so that the generator
maintains an electrical output.
[0003] Control systems are often used to regulate the operation of
gas turbines. In operation, a control system may receive
information about a variety of conditions such as, for example,
pressures, temperatures, fuel flow rates, and engine frequencies,
among others. In response, the control system can make adjustments
to the inputs of the gas turbine engine to maintain desired
performance.
[0004] Over time, sensors used in a gas turbine for monitoring
turbine conditions, including pressure sensors, can become
deficient (i.e., do not provide an accurate or reliable signal),
and as a result, proper monitoring of the gas turbine becomes more
difficult. It is preferable to detect the failure of sensors as
early as possible, to avoid the possibility of the control system
making decisions based on deficient sensor measurements or input
from a failing sensor. Accordingly, an improved method of
determining the health of a sensor in a gas turbine that addresses
these issues, among others, is needed.
SUMMARY
[0005] This summary presents a high-level overview of various
aspects of the invention and a selection of concepts that are
further described below in the detailed description section of this
disclosure. This summary is not intended to identify key or
essential features of the claimed subject matter, nor is it
intended to be used as an aid in isolation to determine the scope
of the claimed subject matter. The scope of the invention is
defined by the claims.
[0006] In brief, and at a high level, this disclosure describes,
among other things, methods and systems for determining that a
sensor, such as a pressure sensor, that provides signals to a
control system of a gas turbine is deficient, or rather, is not
operating correctly or reliably prior to actual failure of the
sensor. In the example of a pressure sensor, the amplitude of the
signal from the pressure sensor may be monitored in different
frequency ranges of the signal in order to detect certain abnormal
conditions of the gas turbine that may require attention, and also,
concurrently and/or separately, monitor the pressure sensor for any
indications of deficiency. By monitoring different frequency ranges
of the sensor signal, a deficiency in the sensor may be detected
prior to actual failure of the sensor, while still monitoring for
particular abnormal conditions of the gas turbine. Various
non-limiting embodiments that achieve this detection are described
in detail herein.
[0007] In a first embodiment, a computer-implemented method,
executed by one or more processors, for detecting deficient sensors
in gas turbines is provided, in accordance with an embodiment of
the present invention. The method comprises receiving pressure
readings from a pressure sensor coupled to a gas turbine,
monitoring a first frequency range of the pressure readings for
abnormal conditions of the gas turbine, monitoring a second
frequency range of the pressure readings for sensor failure
indications, and determining either that the sensor failure
indications are not present and that the monitoring for the
abnormal conditions is being performed by a correctly operating
sensor, or the sensor failure indications are present and that the
monitoring for the abnormal conditions is being performed by a
deficient sensor.
[0008] In a second embodiment, one or more computer-readable media
having computer executable instructions embodied thereon that, when
executed, perform a method for detecting deficient sensors in gas
turbines is provided, in accordance with an embodiment of the
present invention. The method comprises receiving signals from a
sensor in a gas turbine, monitoring a first frequency range of the
signals for abnormal conditions of the gas turbine, monitoring a
second frequency range of the signals for sensor failure
indications, and determining either that the sensor failure
indications are not detected and the sensor is operating correctly,
or the sensor failure indications are detected and the sensor is
deficient. The abnormal conditions may comprise a first range of
sensor readings in the first frequency range, and the sensor
failure indications may comprise at least one of a minimum sensor
reading in the second frequency range and a minimum difference
between concurrent sensor readings in the first frequency range and
in the second frequency range.
[0009] In a third embodiment, a system for detecting deficient
sensors in gas turbines is provided, in accordance with an
embodiment of the present invention. The system comprises a gas
turbine having one or more combustors, a control system
communicatively coupled to the gas turbine, and a sensor coupled to
the gas turbine and communicatively coupled to the control system,
the sensor sending signals to the control system. The control
system may be configured to monitor a first frequency range of the
signals for abnormal conditions of the gas turbine, monitor a
second frequency range of the signals for sensor failure
indications, and determine either that the sensor failure
indications are not detected and the sensor is operating correctly,
or the sensor failure indications are detected and the sensor is
deficient. The abnormal conditions may comprise a first range of
sensor readings in the first frequency range, the sensor failure
indications may comprise a second range of sensor readings in the
second frequency range, and the first frequency range may be higher
than the second frequency range.
[0010] The methods and systems disclosed herein are discussed
frequently in the context of pressure sensors; however, these
methods and systems are applicable to any type of sensor in which
different frequency ranges of the sensor signal may be monitored
for changing conditions.
[0011] Abnormal conditions of the gas turbine may comprise any type
of sensor signal or indication that may warrant reaction,
adjustment, or identification by the control system of the gas
turbine. One such example is flameout of the gas turbine, sometimes
known as Lean Blowout (LBO). LBO can occur when the local
fuel-to-air ratio in the reaction zone of the gas turbine falls
below the lean flammability limit. In such a case, the flame is too
lean to maintain stability, and begins to fluctuate, creating low
frequency acoustic pulsations called LBO tones. Eventually, if such
lean instability continues, the flame in one or more of the
combustion chambers may get extinguished and the turbine will
forcefully shutdown. Indications of LBO may be detected through a
spike in pressure signals from a pressure sensor in a combustor,
for example.
BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWINGS
[0012] Illustrative embodiments of the present invention are
described in detail below with reference to the attached drawing
figures, wherein:
[0013] FIG. 1 is an exemplary system for detecting deficient
sensors in a gas turbine, in accordance with an embodiment of the
present invention;
[0014] FIG. 2A is an exemplary graph indicating feedback from a
properly operating pressure sensor coupled to a gas turbine, in
accordance with an embodiment of the present invention;
[0015] FIG. 2B is an exemplary graph indicating feedback from a
deficient pressure sensor coupled to a gas turbine, in accordance
with an embodiment of the present invention;
[0016] FIG. 2C is an exemplary graph indicating feedback from a
failed pressure sensor coupled to a gas turbine, in accordance with
an embodiment of the present invention;
[0017] FIG. 3 is a block diagram of a first exemplary method for
detecting deficient sensors in a gas turbine, in accordance with an
embodiment of the present invention;
[0018] FIG. 4 is a block diagram of a second exemplary method for
detecting deficient sensors in a gas turbine, in accordance with an
embodiment of the present invention; and
[0019] FIG. 5 is an exemplary computing environment which may be
used with a control system of a gas turbine to detect deficient
sensors, in accordance with an embodiment of the present
invention.
DETAILED DESCRIPTION
[0020] The subject matter of the various embodiments of the present
invention is described with specificity in this disclosure to meet
statutory requirements. However, the description itself is not
intended to limit the scope of invention. Rather, the claimed
subject matter may be embodied in various other ways to include
different features, components, elements, combinations, and/or
steps similar to the ones described in this document, and in
conjunction with other present and future technologies. Terms
should not be interpreted as implying any particular order among or
between various steps unless the stated order of steps is required.
Many different arrangements of the various components depicted, as
well as use of components not shown, are possible without departing
from the scope of the claims.
[0021] At a high level, the present invention generally relates to
systems and methods for detecting deficient sensors, such as
pressure sensors, in a gas turbine system. More specifically,
embodiments of the invention allow a control system of a gas
turbine, which utilizes a sensor to receive signals and feedback
related to the operation of the gas turbine, to detect both
abnormal conditions of the gas turbine and sensor failure
indications (i.e., indications of a deficient sensor) using the
signals from the sensor prior to actual failure of the sensor.
Embodiments allow this to be accomplished through monitoring of
signals from the sensor in different frequency ranges for feedback
that relates to either the abnormal conditions or the sensor
failure indications, depending on the frequency range monitored for
a given signal. Additionally, the frequency ranges, and parameters
relating to certain indications in the frequency ranges, may be
user-configurable, to allow such monitoring in differently
configured gas turbine systems.
[0022] Having described some general aspects of the invention,
reference is now made to FIG. 1, which depicts an exemplary system
100 for detecting deficient sensors in a gas turbine, in accordance
with an embodiment of the present invention. In FIG. 1, the system
100 includes a gas turbine 102 having one or more combustors 104, a
pressure sensor 106 communicatively coupled to the gas turbine 102,
and a control system 108 communicatively coupled to the pressure
sensor 106 and to the gas turbine 102. The control system 108 may
be used to monitor feedback, or rather, signals, from the pressure
sensor 106, and use such feedback in controlling different aspects
of the gas turbine 102. Other components of the system 100 are
possible and contemplated; however, for clarity, only a few
components are shown in FIG. 1. Additionally, the gas turbine 102
shown in FIG. 1 is merely exemplary, and other gas turbine designs
are contemplated.
[0023] Referring now to FIG. 2A, a graph 200 of a signal from a
properly operating pressure sensor connected to a gas turbine is
provided, in accordance with an embodiment of the present
invention. As shown in FIG. 2A, the x-axis 202 of the graph
represents various frequencies of a pressure signal 204 (i.e., a
range of frequencies of the same pressure signal 204) from the
pressure sensor, and the y-axis 206 represents the signal amplitude
of the pressure signal 204 at the different frequencies. The curve
of the pressure signal 204 is low at either end, with an elevated
signal amplitude at point 208. A first frequency range 210, which
for exemplary purposes is 10-50 Hz, is monitored for abnormal
conditions of the gas turbine (e.g., a pressure spike related to
LBO), which may be detected through predetermined activity of the
signal amplitude within the first frequency range 210. A second
frequency range 212, which for exemplary purposes is 0-10 Hz, is
monitored for sensor failure indications, which may be detected
through predetermined activity of the signal amplitude within the
second frequency range 212. The predetermined activity may be any
form of signal activity, including exceeding a minimum signal
amplitude, receiving signals in a predetermined range of signal
amplitudes, or another indication.
[0024] The first frequency range 210 may be selected to allow for
monitoring of specific abnormal conditions of the gas turbine that
require control system input, adjustment, identification, or
reaction (e.g., a certain spike in signal amplitude of the pressure
signal 204 that indicates a gas turbine malfunction or LBO).
Monitoring of pressure readings outside of the first frequency
range 210 may not normally be necessary or practical for detection
of such abnormal conditions of the gas turbine, but readings
outside of the first frequency range 210, such as in the second
frequency range 212, may still provide useful indications of the
health of the pressure sensor. In this respect, sensor failure
indications may be detected in the second frequency range 212 prior
to the pressure sensor becoming fully deficient, and affecting the
readings in the first frequency range 210. As one example, when the
signal amplitude of the pressure signal 204 spikes above a certain
level in the second frequency range 212, the control system may
identify a failing sensor, deactivate the sensor, and/or indicate
that a repair or replacement of the sensor is needed.
[0025] Referring now to FIG. 2B, a graph 201 of a pressure signal
205 with different signal amplitudes measured at different
frequencies of the pressure signal 205 is provided, in accordance
with an embodiment of the present invention. The graph 201 in FIG.
2B shows the pressure signal 205, which is from a pressure sensor
that is deficient or becoming deficient, as discussed herein.
[0026] Furthermore, in FIG. 2B, as discussed with respect to FIG.
2A, the first frequency range 210 is monitored for predetermined
changes in the signal amplitude of the pressure signal 205 within
the first frequency range 210, to identify abnormal conditions of
the gas turbine which require reaction and adjustment by the
control system. The second frequency range 212 is monitored for
predetermined changes in the signal amplitude of the pressure
signal 205 within the second frequency range 212, to identify
sensor failure indications. The sensor failure indications may,
once again, be at least one of a minimum signal amplitude of the
pressure signal 205, detection of a signal amplitude within a
certain range, and/or a relative difference between signal
amplitudes in the first frequency range 210 and the second
frequency range 212, depending on the desired configuration.
Multiple configurations are possible and contemplated.
[0027] In FIG. 2B, a spike 216 in the signal amplitude of the
pressure signal 205 in the second frequency range 212 is present.
This spike 216 indicates that the associated pressure sensor is
deficient, or becoming deficient. Identification of the failing
pressure sensor in the second frequency range 212 allows repair or
replacement of the pressure sensor before the readings in the first
frequency range 210 become compromised or affected, which can
otherwise lead to improper function by the control system of the
gas turbine due to inaccurate or deficient feedback from the
pressure sensor.
[0028] Referring now to FIG. 2C, a graph of pressure signals 207A
and 207B with signal amplitudes shown at various frequencies for a
failed pressure sensor is provided, in accordance with an
embodiment of the present invention. In FIG. 2C, as discussed with
respect to FIG. 2B, the spike 216 in the signal amplitude of the
pressure signal 207A is present. Additionally, the increased signal
amplitude indicating failure of the pressure sensor is now
detectible in both the first frequency range 210 and in the second
frequency range 212 using the pressure signals 207A and 207B. This
shows that the pressure sensor has failed completely. Monitoring of
the second frequency range 212 may allow detection of this failure,
and replacement or repair of the pressure sensor, before this state
of feedback is reached.
[0029] Referring now to FIG. 3, a block diagram of a first
exemplary method 300 for detecting deficient pressure sensors in
gas turbines is provided, in accordance with an embodiment of the
present invention. At a first block 310, pressure readings, such as
the pressure signal 204 shown in FIG. 2A, from a pressure sensor,
such as the pressure sensor 106 shown in FIG. 1, coupled to a gas
turbine, such as the gas turbine 102 shown in FIG. 1, are
received.
[0030] At a second block 312, a first frequency range, such as the
first frequency range 210 shown in FIGS. 2A-2C, of the pressure
readings is monitored for abnormal conditions of the gas turbine,
such as a predetermined spike in signal amplitude, a predetermined
range of signal amplitudes, or another indication. At a third block
314, a second frequency range, such as the second frequency range
212 shown in FIGS. 2A-2C, of the pressure readings is monitored for
sensor failure indications, such as a predetermined spike in signal
amplitude, a predetermined range of signal amplitude, a relative
difference in signal amplitude between the first frequency range
and the second frequency range, or another indication that
indicates that the pressure sensor is approaching failure and is in
a deficient state.
[0031] At a fourth block 316, it is determined either that the
sensor failure indications are not present and that the monitoring
for the abnormal conditions is being performed by a correctly
operating sensor, as shown in FIG. 2A, for example, or the sensor
failure indications are present and that the monitoring for the
abnormal conditions is being performed by a deficient sensor, as
shown in FIG. 2B, for example.
[0032] Referring now to FIG. 4, a block diagram 400 of a second
exemplary method of detecting deficient sensors in gas turbines is
provided, in accordance with an embodiment of the present
invention. At a first block 410, signals, such as the pressure
signal 204 shown in FIG. 2A, from a sensor, such as the sensor 106
shown in FIG. 1, in a gas turbine, such as the gas turbine 102
shown in FIG. 1, are received. At a second block 412, a first
frequency range, such as the first frequency range 210 shown in
FIGS. 2A-2C, of the signals is monitored for abnormal conditions of
the gas turbine.
[0033] At a third block 414, a second frequency range, such as the
second frequency range 212 shown in FIGS. 2A-2C, of the signals is
monitored for sensor failure indications. At a fourth block 416, it
is determined either that the sensor failure indications are not
detected and the sensor is operating correctly, as shown in FIG.
2A, for example, or the sensor failure indications are detected and
the sensor is deficient, as shown in FIG. 2B, for example. The
abnormal conditions of the gas turbine may comprise a first range
of sensor readings in the first frequency range, and the sensor
failure indications may comprise at least one of a minimum sensor
reading in the second frequency range, and a minimum difference
between concurrent sensor readings in the first frequency range and
in the second frequency range.
[0034] The first frequency range may have a predetermined first
range of sensor readings, or signal amplitudes, at which an
abnormal condition of the gas turbine is deemed to occur. The
second frequency range may have a predetermined second range of
sensor readings, or signal amplitudes, at which sensor failure
indications are deemed to occur. The ranges may be actual ranges or
just minimums (e.g., 10-20, or 10 to infinity). The frequency
ranges may be distinct, may be spaced apart, or may overlap.
Multiple frequency ranges may be monitored, as well. The first
range of sensor readings and the second range of sensor readings
may at least partially overlap each other. Alternatively, the
ranges or minimum may be closely sequenced without overlap, or a
monitoring gap between the first and second frequency ranges and/or
the first and second sensor ranges may be utilized to further
target a specific known abnormal reading. Once sensor failure
indications have been detected, the control system may initiate a
response. The response may include flagging or identifying an
associated sensor, possibly for a specific time interval.
Additionally, upon detecting a deficient sensor, the control system
may ignore input from the associated sensor, may disable input from
the sensor, and/or may provide an indication that the sensor is
deficient.
[0035] Detecting that sensor failure indications have occurred may
comprise determining that a first pressure signal amplitude from
the first frequency range and a second pressure signal amplitude
from the second frequency range are at least a predetermined
difference, where the second pressure signal amplitude is greater
than the first pressure signal amplitude. Additionally, the first
frequency range may be at least 10 Hz on its lowest end, and the
second frequency range may be at most 10 Hz on its upper end. Each
of the first frequency range, the second frequency range, the first
range of sensor readings, and the second range of sensor readings
may be user-configurable. Monitoring of abnormal conditions of the
gas turbine and sensor failure indications may occur
simultaneously, alternately, concurrently, or separately. The
system may further include one or more of the same sensors, such as
pressure sensors, whose readings are monitored and/or compared by
the control system.
[0036] Referring now to FIG. 5, an exemplary operating environment
which can be used for implementing embodiments described herein is
shown and designated generally as computing device 500. Computing
device 500 is but one example of a suitable computing environment
and is not intended to suggest any limitation as to the scope of
use or functionality of the invention. The computing device 500
should not be interpreted as having any dependency or requirement
relating to any one or a combination of components illustrated.
[0037] In FIG. 5, computing device 500 includes a bus 510 that
directly or indirectly couples the following devices: memory 512,
one or more processors 514, one or more presentation components
516, input/output (I/O) ports 518, input/output (I/O) components
520, and an illustrative power supply 522. Bus 510 represents what
may be one or more busses (such as an address bus, data bus, or a
combination thereof). Although the various blocks of FIG. 5 are
shown with lines for the sake of clarity, in reality, delineating
various components is not as clear, and metaphorically, the lines
are blurred. For example, one may consider a presentation component
such as a display device to be an I/O component. Also, processors
have memory. The diagram of FIG. 5 is merely illustrative of an
exemplary computing device that can be used in connection with one
or more embodiments of the present invention. Distinction is not
made between such categories as "workstation," "server," "laptop,"
"hand-held device," etc., as all are contemplated as within the
scope of FIG. 5 and when referencing the "computing device."
[0038] The invention may be described in the general context of
computer code or machine-useable instructions, including
computer-executable instructions such as program modules, being
executed by a computer or other machine, such as a personal data
assistant or other handheld device. Generally, program modules
including routines, programs, objects, components, data structures,
etc., refer to code that performs particular tasks or implements
particular abstract data types. The invention may be practiced in
any variety of system configurations, including hand-held devices,
consumer electronics, general-purpose computers, and more specialty
computing devices, among others. The invention may also be
practiced in distributed computing environments where tasks are
performed by remote-processing devices that are linked through a
communications network.
[0039] Computing device 500 may include a variety of
computer-readable media and/or computer storage media.
Computer-readable media may be any available media that can be
accessed by computing device 500 and includes both volatile and
non-volatile media, removable and non-removable media. By way of
example and not limitation, computer-readable media may comprise
computer storage media and communication media and/or devices.
Computer storage media may include volatile and non-volatile,
removable and non-removable media implemented in any method or
technology for storage of information such as computer-readable
instructions, data structures, program modules, or other data.
Computer storage media includes, but is not limited to, RAM, ROM,
EEPROM, flash memory or other memory technology, CD-ROM, digital
versatile disks (DVD) or other optical disk storage, magnetic
cassettes, magnetic tape, magnetic disk storage or other magnetic
storage devices, or any other medium which can be used to store the
desired information and which can be accessed by computing device
500. These memory components can store data momentarily,
temporarily, or permanently. Computer storage media does not
include signals per se.
[0040] Communication media typically embodies computer-readable
instructions, data structures, or program modules. By way of
example, and not limitation, communication media includes wired
media such as a wired network or direct-wired connection, and
wireless media such as acoustic, RF, infrared, and other wireless
media. Combinations of any of the above should also be included
within the scope of computer-readable media.
[0041] Memory 512 includes computer storage media in the form of
volatile and/or non-volatile memory. The memory may be removable,
non-removable, or a combination thereof. Exemplary hardware devices
include solid-state memory, hard drives, optical-disc drives, etc.
Computing device 500 includes one or more processors that read data
from various entities such as memory 512 or I/O components 520.
Presentation component(s) 516 present data indications to a user or
other device. Exemplary presentation components include a display
device, speaker, printing component, vibrating component, etc. I/O
ports 518 allow computing device 500 to be logically coupled to
other devices including I/O components 520, some of which may be
built-in. Illustrative components include a microphone, joystick,
game pad, satellite dish, scanner, printer, wireless device, and
the like.
[0042] Embodiments of the technology have been described herein to
be illustrative rather than restrictive. Alternative embodiments
will become apparent to readers of this disclosure. Further,
alternative means of implementing the aforementioned elements and
steps can be used without departing from the scope of the claims,
as would be understood by one having ordinary skill in the art.
Certain features and sub-combinations are of utility and may be
employed without reference to other features and sub-combinations,
and are contemplated as within the scope of the claims.
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